Battery management system having a plurality of backup communication main units, and aircraft

Abstract

A battery management system having a plurality of backup communication main units, and an aircraft are provided. In the battery management system, a plurality of independent power battery assemblies are provided, and the design of using a plurality of backup communication main units is used; and considering the hardware failure probability and the redundancy margin, some of all battery management units are selected as backup communication main units, thereby improving the fault tolerance rate and reliability of aircraft communication, ensuring that the aircraft reliably acquires battery data required by safe flight, improving the reliability of aircraft power supply management, and guaranteeing the flight safety of the aircraft.

What is claimed is: 
     
         1 . A battery management system having a plurality of backup communication main units, comprising N sets of power battery modules connected in parallel, wherein the N sets of power battery modules connected in parallel comprises N battery management units in total, and among the N battery management units, M battery management units serve as backup communication main units, where M<N, and each of the backup communication main units is configured to forward data from the N sets of power battery modules connected in parallel to a complete ALLCAN network. 
     
     
         2 . The battery management system according to  claim 1 , wherein each power battery module of the N sets of power battery modules comprises a battery management unit, a battery protection component and a power battery pack, wherein the battery protection component comprises a fuse, a Hall current sensor and a relay; wherein within each power battery module, a negative terminal of the power battery pack is connected to a positive busbar of an aircraft, and a positive terminal of the power battery pack is connected to a first end of the fuse, and a second end of the fuse passes through a central hole of the Hall current sensor and is connected to a first contact of the relay, while a second contact of the relay is connected to a negative busbar of the aircraft; wherein a signal acquisition line of the Hall current sensor is connected to the battery management unit to enable real-time current detection; and a coil terminal of the relay is connected to the battery management unit, and the battery management unit controls connection and disconnection of the coil terminal of the relay based on received Controller Area Network (CAN) communication commands, thereby controlling whether the power battery module participates in the aircraft's charging and discharging state. 
     
     
         3 . The battery management system according to  claim 2 , wherein, when a fault or abnormality occurs in a circuit of the power battery pack, a current in the circuit increases, and when the current reaches a melting threshold of the fuse, the fuse automatically melts, disconnecting the circuit. 
     
     
         4 . The battery management system according to  claim 2 , wherein each battery management unit collects and manages the data thereof respective power battery module and transmits the data, wherein the data comprises voltage, current, temperature, State of Charge (SOC) status, and voltage difference. 
     
     
         5 . The battery management system according to  claim 4 , wherein each battery management unit is equipped with a first-channel CAN interface, a second-channel CAN interface and a third-channel CAN interface, wherein the first-channel CAN interface is used for hardware debugging, wherein the second-channel CAN interface is connected to a CAN 2  network, forming an internal CAN network for the battery management system with the N sets of power battery modules of the aircraft, and wherein the third-channel CAN interface is used for communication with external devices and is connected to the complete ALLCAN network. 
     
     
         6 . The battery management system according to  claim 1 , wherein among the M battery management units serving as the backup communication main units, a priority of each of the backup communication main units is determined based on a magnitude of a battery management unit Identification (ID); wherein as the battery management unit ID decreases, the priority of the battery management unit ID increases; and when a current communication main unit fails, a battery management unit ID with a smallest position among the M battery management units is selected as a new communication main unit to forward the data from the N sets of power battery modules connected in parallel to the complete ALLCAN network. 
     
     
         7 . The battery management system according to  claim 1 , wherein the power battery pack comprises lithium-ion polymer cells. 
     
     
         8 . The battery management system according to  claim 7 , wherein a pack housing of the power battery pack is reinforced with 1.0 mm-thick fire-resistant fiberglass plates and comprises an internal temperature sensor, and the power battery pack is installed inside a chassis of the aircraft with flexible mounting. 
     
     
         9 . A method of reserving backup communication main units, wherein the method being used for selecting a backup communication main unit in a battery management system, comprises the following steps:
 S 1 : setting a battery management unit ID in the battery management system;   S 2 : using a magnitude of the battery management unit ID as a standard for setting a priority of the backup communication main unit, wherein as the battery management unit ID decreases, the priority of the battery management unit ID increases;   S 3 : confirming whether a current communication main unit in the battery management system has failed, and when the current communication main unit failed, selecting the battery management unit ID with a smallest position, among M battery management units, as a new communication main unit; and   S 4 : allowing the new communication main unit to forward the data from N sets of power battery modules connected in parallel to a complete ALLCAN network.   
     
     
         10 . An aircraft, comprising the battery management system according to  claim 1 . 
     
     
         11 . The aircraft according to  claim 10 , wherein in the battery management system, each power battery module of the N sets of power battery modules comprises a battery management unit, a battery protection component and a power battery pack, wherein the battery protection component comprises a fuse, a Hall current sensor and a relay; wherein within each power battery module, a negative terminal of the power battery pack is connected to a positive busbar of an aircraft, and a positive terminal of the power battery pack is connected to a first end of the fuse, and a second end of the fuse passes through a central hole of the Hall current sensor and is connected to a first contact of the relay, while a second contact of the relay is connected to a negative busbar of the aircraft; wherein a signal acquisition line of the Hall current sensor is connected to the battery management unit to enable real-time current detection; and a coil terminal of the relay is connected to the battery management unit, and the battery management unit controls connection and disconnection of the coil terminal of the relay based on received CAN communication commands, thereby controlling whether the power battery module participates in the aircraft's charging and discharging state. 
     
     
         12 . The aircraft according to  claim 11 , wherein in the battery management system, when a fault or abnormality occurs in a circuit of the power battery pack, a current in the circuit increases, and when the current reaches a melting threshold of the fuse, the fuse automatically melts, disconnecting the circuit. 
     
     
         13 . The aircraft according to  claim 11 , wherein in the battery management system, each battery management unit collects and manages the data thereof respective power battery module and transmits the data, wherein the data comprises voltage, current, temperature, SOC status, and voltage difference. 
     
     
         14 . The aircraft according to  claim 13 , wherein in the battery management system, each battery management unit is equipped with a first-channel CAN interface, a second-channel CAN interface and a third-channel CAN interface, wherein the first-channel CAN interface is used for hardware debugging, wherein the second-channel CAN interface is connected to a CAN 2  network, forming an internal CAN network for the battery management system with the N sets of power battery modules of the aircraft, and wherein the third-channel CAN interface is used for communication with external devices and is connected to the complete ALLCAN network. 
     
     
         15 . The aircraft according to  claim 10 , wherein in the battery management system, among the M battery management units serving as the backup communication main units, a priority of each of the backup communication main units is determined based on a magnitude of a battery management unit ID; wherein as the battery management unit ID decreases, the priority of the battery management unit ID increases; and when a current communication main unit fails, a battery management unit ID with a smallest position among the M battery management units is selected as a new communication main unit to forward the data from the N sets of power battery modules connected in parallel to the complete ALLCAN network. 
     
     
         16 . The aircraft according to  claim 10 , wherein in the battery management system, the power battery pack comprises lithium-ion polymer cells. 
     
     
         17 . The aircraft according to  claim 16 , wherein in the battery management system, a pack housing of the power battery pack is reinforced with 1.0 mm-thick fire-resistant fiberglass plates and comprises an internal temperature sensor, and the power battery pack is installed inside a chassis of the aircraft with flexible mounting.